Exhaust mixer for turbofan aeroengine

• US 4,487,017 A
• Filed: 08/13/1982
• Issued: 12/11/1984
• Est. Priority Date: 09/03/1981
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Rodgers, Leonard J.
• Primary Examiner(s): Croyle, Carlton R.
• Assistant Examiner(s): Simenauer, Jeffrey A.
• Application Number:
  US06/408,133
• Time in Patent Office: 851 Days
• Field of Search: 60/262, 60/264, 60/271, 181/220, 181/222, 181/213, 239/265.17, 239/265.19, 239/265.13, 239/127.3
• US Class Current: 60/262
• CPC Class Codes: F02K 1/386 mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
• CPC Class Codes: F02K 1/48 Corrugated nozzles
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An exhaust mixer for a turbofan aeroengine can be classified as being of the multi-lobed type, with troughs between the lobes. Good mixing efficiency together with good aerodynamics, short axial length and low weight is achieved by forming the mixer from flow surfaces which are longitudinally twisted between their upstream and downstream ends, opposing sides of each lobe and trough being of opposite twist. Between the upstream and downstream ends of the twisted flow surfaces, their latitudinal contours become approximately S-shaped so as to define outer portions of the lobes, inner portions of the troughs and the opposed sides of the lobes and troughs.

Claims

1. For a turbofan aeroengine, an exhaust mixer of the type comprising a plurality of lobes, through which portions of a turbine exhaust stream pass, and a plurality of troughs defined between said lobes, through which troughs portions of a fan air stream pass, said lobes and said troughs being at least partially defined by turbine exhaust stream contacting flow surfaces and fan air stream contacting flow surfaces respectively whereby each said lobe and each said trough has generally opposed sides extending longitudinally of said turbine exhaust and fan air streams, one such side of each of said lobes and troughs comprising a flow surface portion having a longitudinal clockwise progressive twist between its upstream and downstream ends and the other such side of each of said lobes and troughs comprising a flow surface portion having a similar but anticlockwise twist, said flow surfaces being shaped such that latitudinal contours of said flow surfaces at a succession of stations downstream of their upstream ends are sinuous shapes each with a single inflexion, said sinuous latitudinal contours having outwardly convex portions which at least partly delineate outer portions of said lobes, inwardly concave portions which at least partly delineate inner portions of said troughs, and intermediate portions between said outwardly convex and inwardly concave portions, which intermediate portions at least partially delineate said opposed sides of said lobes and troughs.

4. An exhaust mixer according to any one of claims 1 to 3 in which said latitudinal contours of said flow surfaces steadily change from said sinuous shapes at a succession of stations intermediate said upstream and downstream ends of said flow surfaces, to uninflected curves at a succession of stations approaching said downstream ends of said flow surfaces, said uninflected curves having outwardly extending portions which at least partly delineate downstream portions of said opposed sides of said lobes and troughs, and inwardly concave portions which at least partly delineate downstream inner portions of said troughs.

5. An exhaust mixer according to any one of claims 1 to 3 in which said progressive twist between said upstream and downstream ends of said flow surfaces is non-uniform in that the degree of twist per unit length of said flow surfaces is greater near their downstream ends than at their upstream ends.

6. An exhaust mixer according to any one of claims 1 to 3 in which peripherally adjacent ones of said flow surfaces are not contiguous with each other over at least their downstream portions, whereby said outer portions of said lobes and said inner portions of said troughs are provided with substantially V-shaped gashes extending convergently upstream from the downstream ends of said lobes and troughs.

7. An exhaust mixer according to any one of claims 1 to 3 in which said downstream ends of said flow surface portions comprising said inner portions of said troughs are further downstream than said downstream ends of said flow surface portions comprising said outer portions of said lobes.

8. An exhaust mixer according to anyone of claims 1 to 3 in which said flow surfaces have downstream edges composed of straight lines.

9. An exhaust mixer according to claim 8 in which said downstream edge of each said flow surface is substantially Z-shaped when seen in endelevation.

2. For a turbofan aeroengine, an exhaust mixer having turbine exhaust stream contacting flow surfaces which together at least partially define lobes through which portions of said turbine exhaust stream pass, and fan air stream contacting flow surfaces which together at least partially define troughs between said lobes through which troughs portions of said fan air stream pass, said flow surfaces having a longitudinal and progressive twist between their upstream and downstream ends such that opposing sides of each said lobe and each said trough comprise flow surface portions having opposed senses of twist and the shape of said flow surfaces being such that transverse of the stream-wise direction latitudinal contours of said flow surfaces at a succession of stations downstream of their upstream ends are sinuous shapes each with a single inflexion, said sinuous latitudinal contours having outwardly convex portions which at least partly delineate outer portions of said lobes, inwardly concave portions which at least partly delineate inner portions of said troughs, and intermediate portions between said outwardly convex and inwardly concave portions, which intermediate portions at least partially delineate said opposed sides of said lobes and troughs.

3. An exhaust mixer of the multi-lobed type for a turbofan aeroengine, wherein portions of the turbine exhaust stream pass through the lobes, and portions of the fan air stream pass through troughs between said lobes, each lobe and each trough being at least partially defined by flow surfaces having upstream and downstream ends, said flow surfaces having latitudinal contours transverse of the streamwise direction which steadily change from uninflected curves extending peripherally of said turbine exhaust stream at said upstream ends of said flow surfaces, to sinuous curves with a single inflexion at a succession of stations downstream of said upstream ends of said flow surfaces, said flow surfaces having progressive longitudinal twist between their upstream and downstream ends such that opposing sides of each lobe and each trough comprise flow surface portions having opposed senses of twist, said opposed sides being at least partially delineated by mid-portions of said sinuous curves, outer portions of said lobes being at least partly delineated by outwardly convex portions of said sinuous curves, and inner portions of said troughs being at least partly delineated by inwardly concave portions of said sinuous curves.